EP0282784A2 - Installation de turbine à gaz pour hélicoptères - Google Patents

Installation de turbine à gaz pour hélicoptères Download PDF

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Publication number
EP0282784A2
EP0282784A2 EP88102780A EP88102780A EP0282784A2 EP 0282784 A2 EP0282784 A2 EP 0282784A2 EP 88102780 A EP88102780 A EP 88102780A EP 88102780 A EP88102780 A EP 88102780A EP 0282784 A2 EP0282784 A2 EP 0282784A2
Authority
EP
European Patent Office
Prior art keywords
reduction gear
gas turbine
engine
gear
turbine system
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP88102780A
Other languages
German (de)
English (en)
Other versions
EP0282784A3 (en
EP0282784B1 (fr
Inventor
Wolfgang Weiler
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MTU Aero Engines AG
Original Assignee
MTU Motoren und Turbinen Union Muenchen GmbH
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by MTU Motoren und Turbinen Union Muenchen GmbH filed Critical MTU Motoren und Turbinen Union Muenchen GmbH
Publication of EP0282784A2 publication Critical patent/EP0282784A2/fr
Publication of EP0282784A3 publication Critical patent/EP0282784A3/de
Application granted granted Critical
Publication of EP0282784B1 publication Critical patent/EP0282784B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/04—Helicopters
    • B64C27/12—Rotor drives
    • B64C27/14—Direct drive between power plant and rotor hub
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D35/00—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the invention relates to a gas turbine system according to the preamble of patent claim 1.
  • a significant disadvantage of the known system would be the exclusive application-specificity to a specific aircraft type, i.e. that is, the base engine can practically not be used with regard to different speed requirements for different helicopter or wing-based aircraft types.
  • the invention has for its object to provide a gas turbine system according to the type mentioned (preamble of claim 1), in which the gas turbine engine is arranged at a significantly reduced distance from the rotor main gear.
  • the invention enables a significantly reduced length distance between the base engine and the main rotor gear, as a result of which the center of gravity of the engine can be shifted significantly further towards the center of gravity of the aircraft.
  • the considerable gain in the reduced overall length of the system is achieved by utilizing the space between the base engine and the reduction gear, which is otherwise caused by a so-called "far wave", for integrating the articulated compensating device which is normally associated with a considerable system length.
  • the reduction gear is non-positively rigidly linked to the main rotor gear in a short axial way. Mutual misalignment is thus compensated for between the base engine on one side and the main rotor gear together with the reduction gear of the engine on the other side.
  • the joint lock for the gimbal-coupled part of the compensating device which is also possible according to claim 10, permits the same properties as the previously known construction methods with regard to transport and engine handling during installation and removal.
  • the gas turbine system of a helicopter shown schematically in FIG. 1, has a reduction gear 3 and an articulated compensating device 4 for transmitting the shaft power of a base engine 1 to a helicopter main gear 2, which compensates for mutual positional misalignment between the engine 1 and the helicopter main gear 2.
  • the reduction gear 3 is designed as an autonomous engine module. In such a system, it is new and inventive that the reduction gear 3 is directly non-positively rigidly coupled to the helicopter main gear 2 and that the articulated compensation device 4 is arranged and designed between the base engine 1 and the reduction gear 3.
  • the lifting rotor equipped with helicopter propeller blades, the axis of which is designated 5, is driven via the main rotor gear 2.
  • the reduction gear 3 of the engine is rigidly flanged to the main rotor gear 2 by means of corresponding housing shells 6, 7.
  • the platform-like roof 8 of the helicopter on which the gas turbine system is mounted can be seen in FIG. 1 in such a way that the base engine 1, including the other components that transmit the engine power, are inclined slightly from the top outside towards the bottom and with the axis 5 form an angle of> 90 degrees.
  • the shaft power is taken from the front of the base engine 1 and transmitted from there. 1 also shows an additional module 9 of the base engine 1 which contains the reduction gear 3, the compensation device 4 and the engine inlet 10.
  • the gas turbine system in front of the main helicopter gearbox, in such a way that the shaft power is taken from the rear side of the base engine and transmitted from there.
  • the additional module for the base engine could then contain the reduction gear, the compensation device and at least parts of the exhaust system.
  • Fig. 2 embodies a schematically illustrated longitudinal section of the base engine 1.
  • the gas generator of the base engine 1 contains a combined axial-radial compressor 11, a reversing ring combustion chamber 12 and a compressor drive turbine 13, which have a common Hollow shaft 14 drives the compressor 11.
  • the exhaust gas flow from the compressor drive turbine 13 acts and drives a freely running useful power turbine 15 (two-stage), which sits on a central turbine inner shaft 16, which is guided through the hollow shaft 14 of the gas generator and into the region of the compressor inlet. The shaft power is thus removed at point 17.
  • FIG. 3 illustrates details of the reduction gear 3 of the engine, which is designed as a self-sufficient module, the essential part of the transmission oil system being broken down from the module of the reduction gear 3 and accommodated in a separate module according to FIG. 4.
  • the entire oil system for supplying the reduction gear 3 could also be contained in this separate module.
  • the arrangement of this separate module which is preferably arranged here in the vicinity of the helicopter main transmission 2, is embodied by the box 18.
  • This arrangement of the box 18 or separate module in the vicinity of the main gear 2, or in an area between the reduction gear 3 and main gear 2 makes a further contribution to shifting the gas turbine center of gravity in the direction of the axis 5 of the lifting rotor.
  • the module of the reduction gear 3 contains a pair of intermeshing gear wheels 20, 21 arranged in a gear housing 19 and reducing the inflating engine speed (n Twk ).
  • a pump housing 22 located on the rear of the gear housing 19 contains oil pumps 23, 24 driven by the gear wheel 21 are arranged locally isolated from each other.
  • the separate module according to FIG. 4 or box 18 contains essential elements of the oil system such as an oil tank 25, an air / oil cooler 26, a cooler fan 27 and a hydraulic drive motor 28 of the cooler fan 27.
  • an oil tank 25 an oil tank 25
  • an air / oil cooler 26 a cooler fan 27
  • a hydraulic drive motor 28 of the cooler fan 27 instead of the hydraulic one Drive motor 28 could e.g. B.
  • An electric drive motor can also be provided.
  • modules according to FIGS. 3 and 4 are arranged separately, they are in a functional relationship to one another in the context of the transmission oil supply.
  • the oil pump 23 pumps the oil flowing in via the line 29 into the transmission housing 19 - feed lines 30, 31 - and into the hydraulic drive motor 28 - feed lines 30, 32.
  • the other oil pump 24 promotes this from the Transmission housing 19 oil flowing in via line 33 back into tank 25 via another line 34. From the hydraulic drive motor 28, the oil also always flows back into the tank 25 via a further return line 35.
  • the articulated, elastic compensation device 4 (FIG. 5) contains an angularly movable universal joint coupling 36 between two adjoining ends of tubular parts 37, 38 (collectively also referred to at the beginning as the “outer part” of the housing-shaft connection).
  • One tubular part 37 is flanged at the outer end to a housing extension 39 of the engine reduction gear 3.
  • the other tube part 38 is flanged at the outer end to a shaft end part 40 of the base engine which is adjacent on the shaft output side.
  • the compensating device 4 contains an inner propshaft 41 which has membrane bodies 42, 43 welded into the tubular flesh in the region of both outer ends, which project radially and are arranged at a distance from one another.
  • the membranes 42, 43 each form non-positive, flexurally elastic shaft joint connections and at the same time have a vibration-damping function. 1 or 5, the compensating device 4 is arranged coaxially to the extended axis of the base engine in the non-positive or housing-side coupled out-of-service situation.
  • connection between the inner propeller shaft 41 and the reduction gear 3 can also be made very simply by means of a shaft plug-in connection, that is to say, for example, according to FIG. 5, the flange-like end 44 of the gearbox input shaft is pushed into the sleeve-shaped flange end 45 of the propeller shaft 41, the non-positive connection z. B. by means of bolts along z. B. the line 46 can be done.
  • the remaining end 47 of the cardan shaft assembly 41 can then also be non-positively coupled to the end 17 (see also FIG. 2) of the turbine shaft 16 in the manner described as a plug-on or flange-like arrangement.
  • a locking device of the two cardanically connected pipe parts 37, 38 is proposed, which according to FIG. 6 consists for example of a rod 48, which in Longitudinal pipe direction (arrow F) is pushed through eyelets 49.
  • the reduction gear 3 is quasi rigidly blocked with the base engine 1 and a loose "fluttering" is prevented (transport lock).
  • the invention is also suitable for the use of two or more gas turbine engines by aircraft, in particular helicopters.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • General Details Of Gearings (AREA)
  • Gear Transmission (AREA)
  • Catching Or Destruction (AREA)
  • Transition And Organic Metals Composition Catalysts For Addition Polymerization (AREA)
  • Feedback Control In General (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)
EP88102780A 1987-03-17 1988-02-25 Installation de turbine à gaz pour hélicoptères Expired - Lifetime EP0282784B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19873708596 DE3708596A1 (de) 1987-03-17 1987-03-17 Gasturbinenanlage fuer hubschrauber
DE3708596 1987-03-17

Publications (3)

Publication Number Publication Date
EP0282784A2 true EP0282784A2 (fr) 1988-09-21
EP0282784A3 EP0282784A3 (en) 1990-01-24
EP0282784B1 EP0282784B1 (fr) 1993-04-28

Family

ID=6323254

Family Applications (1)

Application Number Title Priority Date Filing Date
EP88102780A Expired - Lifetime EP0282784B1 (fr) 1987-03-17 1988-02-25 Installation de turbine à gaz pour hélicoptères

Country Status (4)

Country Link
US (1) US4899959A (fr)
EP (1) EP0282784B1 (fr)
JP (1) JPS63230928A (fr)
DE (2) DE3708596A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2756542A1 (fr) * 1996-11-29 1998-06-05 Eurocopter France Installation de montage d'un moteur sur un plancher, et de connexion de son arbre de sortie avec au moins un mecanisme entraine
EP2052967A1 (fr) 2007-10-26 2009-04-29 Eurocopter Amélioration aux giravions équipés de turbomoteurs
FR3047471A1 (fr) * 2016-02-08 2017-08-11 Hispano - Suiza Chaine motrice
FR3146658A1 (fr) * 2023-03-16 2024-09-20 Safran Aircraft Engines Ensemble comprenant un tronçon d’arbre guidÉ par un palier maintenu de manière flexible

Families Citing this family (15)

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Publication number Priority date Publication date Assignee Title
US6364249B1 (en) 1999-09-30 2002-04-02 Pratt & Whitney Canada Corp. Engine integrated with rotary wing aircraft transmission
US6394387B1 (en) 2000-12-22 2002-05-28 Pratt & Whitney Canada Corp. Rotor shaft support and drive arrangement
WO2004026689A1 (fr) * 2002-09-17 2004-04-01 Bell Helicopter Textron Inc. Systeme de montage de moteurs decouples en torsion
RU2418936C2 (ru) 2005-12-20 2011-05-20 Канриг Дриллинг Текнолоджи, Лтд. Верхний привод и способ бурения с использованием его
US20100014977A1 (en) * 2008-07-15 2010-01-21 Shattuck Colman D Variable pitch aft propeller vane system
US8347637B2 (en) 2010-05-25 2013-01-08 United Technologies Corporation Accessory gearbox with internal layshaft
FR2961260B1 (fr) * 2010-06-15 2014-05-02 Turbomeca Architecture de turbomoteur non lubrifie
US8602717B2 (en) * 2010-10-28 2013-12-10 United Technologies Corporation Compression system for turbomachine heat exchanger
US8978351B2 (en) * 2011-10-21 2015-03-17 United Technologies Corporation Integrated thermal management system and environmental control system for a gas turbine engine
US8966875B2 (en) * 2011-10-21 2015-03-03 United Technologies Corporation Constant speed transmission for gas turbine engine
US9890591B2 (en) 2013-07-15 2018-02-13 Nabors Drilling Technologies Usa, Inc. Top drive module connector and methods
PL3097291T3 (pl) * 2014-01-20 2021-07-19 United Technologies Corporation Silnik turbospalinowy z przekładnią redukcyjną ze zmniejszoną wielkością zbiornika oleju
US10323473B2 (en) 2014-12-10 2019-06-18 Nabors Industries, Inc. Modular racker system for a drilling rig
US9739071B2 (en) 2015-02-27 2017-08-22 Nabors Industries, Inc. Methods and apparatuses for elevating drilling rig components with a strand jack
EP3929078B1 (fr) * 2020-06-25 2022-08-03 LEONARDO S.p.A. Hélicoptère

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CH337081A (fr) * 1957-03-01 1959-03-15 Armstrong Siddeley Motors Ltd Groupe moteur d'hélicoptère entraîné par turbine à gaz
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Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2756542A1 (fr) * 1996-11-29 1998-06-05 Eurocopter France Installation de montage d'un moteur sur un plancher, et de connexion de son arbre de sortie avec au moins un mecanisme entraine
US6019313A (en) * 1996-11-29 2000-02-01 Eurocopter Installation for mounting an engine on a deck and for connecting its output shaft to at least one driven mechanism
EP2052967A1 (fr) 2007-10-26 2009-04-29 Eurocopter Amélioration aux giravions équipés de turbomoteurs
FR2922860A1 (fr) * 2007-10-26 2009-05-01 Eurocopter France Amelioration aux giravions equipes de turbomoteurs
FR3047471A1 (fr) * 2016-02-08 2017-08-11 Hispano - Suiza Chaine motrice
WO2017137690A1 (fr) * 2016-02-08 2017-08-17 Safran Transmission Systems Chaîne motrice
RU2720760C2 (ru) * 2016-02-08 2020-05-13 Сафран Трансмишн Системз Приводная система
US10875634B2 (en) 2016-02-08 2020-12-29 Safran Transmission Systems Drive train
FR3146658A1 (fr) * 2023-03-16 2024-09-20 Safran Aircraft Engines Ensemble comprenant un tronçon d’arbre guidÉ par un palier maintenu de manière flexible

Also Published As

Publication number Publication date
JPS63230928A (ja) 1988-09-27
EP0282784A3 (en) 1990-01-24
US4899959A (en) 1990-02-13
DE3880535D1 (de) 1993-06-03
EP0282784B1 (fr) 1993-04-28
DE3708596A1 (de) 1988-09-29

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